CN214608059U - Special VTOL unmanned aerial vehicle of unmanned on duty system - Google Patents

Abstract

The utility model discloses a special VTOL unmanned aerial vehicle of unmanned on duty system, the both sides of fuselage are provided with first wing and second wing respectively, can dismantle on the first wing and be connected with first tie-beam, can dismantle on the second wing and be connected with the second tie-beam, the both ends of first tie-beam and the both ends of second tie-beam are equallyd divide and do not are provided with perpendicular screw, the afterbody of fuselage is provided with the afterbody screw, the bottom of fuselage is provided with the outage ware, the lower surface of fuselage still is provided with the undercarriage, the lower extreme of undercarriage is provided with the charging seat. The effect is as follows: this unmanned aerial vehicle has realized remote control: the network is used for data transmission, the transmission distance is not limited, the data transmission is not shielded by barriers, and operators do not need to go to the site for operation; the operation is simple: executing a task by one key and automatically landing; high intellectualization: accurate landing of unmanned aerial vehicle is realized through accurate landing technique, and the aircraft charges, goes up the electricity, the outage all shuts down the cabin through intelligence and independently accomplishes.

Description

Special VTOL unmanned aerial vehicle of unmanned on duty system

Technical Field

The utility model relates to an unmanned air vehicle technique field, concretely relates to unmanned on duty system's special VTOL unmanned aerial vehicle.

Background

Along with the development of unmanned aerial vehicle manufacturing technology and control technology, the application of unmanned aerial vehicle has been introduced in more and more fields, current unmanned aerial vehicle carries on cloud platform camera, carry out conventional observation, need fly to near target area control cloud platform position confirm the approximate position of target location and fix a position again when monitoring, enlarge, fix a position and continue to enlarge, the step is many, the operation complexity is little when the single-point is monitored, but lack the method that high-efficient location was patrolled and examined when needing unmanned aerial vehicle to carry out the multiple spot location to patrol and examine, need adjust repeatedly and do not have the memory function to the position of having patrolled and examined when the multiple spot location is patrolled and examined, need carry out secondary control and just can patrol and examine when patrolling and examining again, inefficiency. Many rotors unmanned on duty system belongs to emerging application mode, and through its application, reducible personnel drop into, improve the operating efficiency, for many rotors unmanned aerial vehicle promote by a large scale and provide powerful guarantee, provide a more convenient, intelligent solution for application environment such as highway, urban road, security protection warehouse, petroleum pipeline, coast patrol.

There is no dedicated vertical take-off and landing drone for unattended systems.

SUMMERY OF THE UTILITY MODEL

Therefore, the utility model provides a special VTOL unmanned aerial vehicle of unmanned on duty system to solve the above-mentioned problem among the prior art.

In order to achieve the above object, the present invention provides the following technical solutions:

according to the first aspect of the utility model, a special vertical take-off and landing unmanned aerial vehicle of an unattended system comprises a body, a first wing, a second wing, a first connecting beam, a second connecting beam, a vertical propeller, a tail propeller, a landing gear, a charging seat and a circuit breaker, the first wing and the second wing are respectively arranged on two sides of the fuselage, the first connecting beam is detachably connected on the first wing, the second wing is detachably connected with the second connecting beam, the two ends of the first connecting beam and the two ends of the second connecting beam are respectively provided with the vertical propellers, the tail part of the machine body is provided with the tail propeller, the bottom of the machine body is provided with the breaker, the lower surface of fuselage still is provided with the undercarriage, the lower extreme of undercarriage is provided with the charging seat.

The tail wing is detachably connected to the rear ends of the first connecting beam and the second connecting beam; the first connecting beam is perpendicular to the extending direction of the first wing, and the second connecting beam is perpendicular to the extending direction of the second wing; the first connecting beam is connected to the middle of the first wing through a bolt, and the second connecting beam is connected to the middle of the second wing through a bolt.

Furthermore, wing spoilers are respectively arranged on the first wing and the second wing, the wing spoilers on the first wing are positioned on the outer side of the first connecting beam, the wing spoilers on the second wing are positioned on the outer side of the second connecting beam, and the first connecting beam and the second connecting beam are symmetrically arranged about the vertical central plane of the fuselage.

The tail fin is of an inverted V-shaped structure, and the end parts of the open ends of the inverted V-shaped structure of the tail fin are detachably arranged at the rear ends of the first connecting beam and the second connecting beam respectively; the tail fin is provided with two tail spoilers which are respectively arranged on two side plates of the inverted V-shaped structure.

Furthermore, the number of the undercarriage is two, the lower part of the body is detachably connected with the two undercarriage, the undercarriage is of a two-point supporting structure, and the two lower end sleeves of the undercarriage are provided with the charging seats.

And the two ends of the undercarriage are connected through the connecting rods respectively, and the connecting rods are positioned below the charging seats.

Further, the machine body is formed by die pressing of high-strength glass fiber and a foam interlayer.

Furthermore, the charging seat comprises a charging seat body and an electrode, the electrode is arranged on the lower surface of the charging seat body, and the charging seat body is provided with a mounting hole which is detachably connected to an undercarriage of the unmanned aerial vehicle; the lower surface of the charging seat body is provided with a groove, and the electrode is arranged in the groove; the groove is an open rectangular cross-section groove; the electrode is a rectangular columnar bulge and is arranged at the center of the groove.

The charging seat body is provided with a plurality of charging holes, and the charging seat body is provided with a plurality of charging holes; the mounting hole is a rectangular hole; the dihedral angle between the plane of the clamping piece and the plane of the charging seat body is an obtuse angle; the clamping piece is of a U-shaped structure, the mounting hole is formed between the open end of the U-shaped structure of the clamping piece and the charging seat body, four fixing holes are formed in the clamping piece, the fixing holes are stepped holes, and the fastening screws are connected in the fixing holes in a threaded mode; the nominal diameter of the fastening screw is between 3mm and 5 mm.

Further, still include the visor, be equipped with the locating hole on the visor, the charging seat body deviates from the mounting groove has been seted up on the surface of recess, the visor is established the open end of mounting groove, the mounting groove is used for installing the circuit board.

The utility model has the advantages of as follows:

1. this unmanned aerial vehicle has realized remote control: the network is used for data transmission, the transmission distance is not limited, the data transmission is not shielded by barriers, and operators do not need to go to the site for operation;

2. this unmanned aerial vehicle easy operation: one key is used for executing tasks, autonomous landing is realized, the flight control adopts an instruction key type design to reduce the requirement on operators, and the operator training can be completed within 2 h;

3. this unmanned aerial vehicle is highly intelligent: accurate landing of unmanned aerial vehicle is realized through accurate landing technique, and the aircraft charges, goes up the electricity, the outage all shuts down the cabin through intelligence and independently accomplishes.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It should be apparent that the drawings in the following description are merely exemplary, and that other embodiments can be derived from the drawings provided by those of ordinary skill in the art without inventive effort.

The structure, ratio, size and the like shown in the present specification are only used for matching with the content disclosed in the specification, so as to be known and read by people familiar with the technology, and are not used for limiting the limit conditions which can be implemented by the present invention, so that the present invention has no technical essential significance, and any structure modification, ratio relationship change or size adjustment should still fall within the scope which can be covered by the technical content disclosed by the present invention without affecting the efficacy and the achievable purpose of the present invention.

Fig. 1 is the utility model discloses some embodiments provide a special VTOL unmanned aerial vehicle's of unmanned on duty system stereogram.

Fig. 2 is a front view of the dedicated vertical take-off and landing drone of the unattended system according to some embodiments of the present invention.

Fig. 3 is a top view of the dedicated vtol drone of the unattended system according to some embodiments of the present invention.

Fig. 4 is a bottom view of the special vertical take-off and landing unmanned aerial vehicle of the unattended system provided by some embodiments of the present invention.

Fig. 5 is a front view of a dedicated vtol drone of an unattended system according to some embodiments of the present invention.

Fig. 6 is a rear view of a dedicated vtol drone of an unattended system according to some embodiments of the present invention.

Fig. 7 is a charging seat perspective view of the dedicated vertical take-off and landing unmanned aerial vehicle of the unattended system provided by some embodiments of the present invention.

Fig. 8 is a charging seat plan view of the dedicated vtol unmanned aerial vehicle of the unattended system according to some embodiments of the present invention.

In the figure: 1. fuselage, 2, first wing, 3, second wing, 4, first tie-beam, 5, second tie-beam, 6, perpendicular screw, 7, tail screw, 8, fin, 9, undercarriage, 10, connecting rod, 11, outage ware, 12, charging seat, 13, charging seat body, 14, joint spare, 15, visor, 16, locating hole, 17, mounting hole, 18, fixed orifices, 19, fastening screw, 20, recess, 21, electrode.

Detailed Description

The present invention is described in terms of specific embodiments, and other advantages and benefits of the present invention will become apparent to those skilled in the art from the following disclosure. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

As shown in fig. 1 to 8, a special vertical take-off and landing unmanned aerial vehicle for an unattended system in an embodiment of the first aspect of the invention includes a fuselage 1, a first wing 2, a second wing 3, a first connecting beam 4, a second connecting beam 5, perpendicular screw 6, tail screw 7, undercarriage 9, charging seat 12 and outage ware 11, the both sides of fuselage 1 are provided with first wing 2 and second wing 3 respectively, can dismantle on the first wing 2 and be connected with first tie-beam 4, can dismantle on the second wing 3 and be connected with second tie-beam 5, the both ends of first tie-beam 4 and the both ends of second tie-beam 5 are equallyd divide and do not are provided with perpendicular screw 6, the afterbody of fuselage 1 is provided with tail screw 7, the bottom of fuselage 1 is provided with outage ware 11, the lower surface of fuselage 1 still is provided with undercarriage 9, the lower extreme of undercarriage 9 is provided with charging seat 12.

In the above embodiment, it should be noted that the vertical propeller 6 realizes vertical take-off and landing of the vertical take-off and landing fixed-wing drone, and the tail propeller 7 realizes horizontal flight of the vertical take-off and landing fixed-wing drone.

The technical effects achieved by the above embodiment are as follows: the unmanned aerial vehicle can vertically take off and land in the mode of a rotor unmanned aerial vehicle, and can cruise in the mode of a fixed-wing unmanned aerial vehicle; in the vertical takeoff and landing process, the unmanned aerial vehicle vertically takes off or lands by utilizing rotors distributed on the unmanned aerial vehicle, when the unmanned aerial vehicle needs to fly in a fixed wing mode, the unmanned aerial vehicle is accelerated to a certain speed in a multi-rotor flight mode, the flight mode is switched, and the unmanned aerial vehicle is propelled by horizontal propulsion power to keep horizontal flight; the folding type air-conditioning unit has the characteristics of portability, long endurance, high reliability, simple and convenient operation, modularization, light structural weight and high strength, and can be placed in an air transport box after being folded for convenient transportation; by arranging the charging seat 12, the unmanned aerial vehicle can be charged quickly; be used for cutting off the power supply for unmanned aerial vehicle through setting up outage ware 11, after unmanned aerial vehicle flies back to the cabin, outage ware 11 on the fuselage 1 and the outage in the cabin part contact back, will automatic power off.

Optionally, as shown in fig. 1 to 8, in some embodiments, the connecting structure further includes a tail 8, and the tail 8 is detachably connected to the rear ends of the first connecting beam 4 and the second connecting beam 5; the first connecting beam 4 is perpendicular to the extending direction of the first wing 2, and the second connecting beam 5 is perpendicular to the extending direction of the second wing 3; the first connecting beam 4 is connected to the middle of the first wing 2 through a bolt, and the second connecting beam 5 is connected to the middle of the second wing 3 through a bolt.

The beneficial effects of the above alternative embodiment are: can dismantle the rear end of connection at first tie-beam 4 and second tie-beam 5 through setting up fin 8, realized dismantling fin 8 and accomodate, can put into convenient transportation in the air transportation case after being convenient for folding, improved the convenience of transportation, reduced the space size that occupies.

Alternatively, as shown in fig. 1 to 8, in some embodiments, each of the first wing 2 and the second wing 3 is provided with a wing spoiler, the wing spoilers on the first wing 2 are located outside the first connecting beam 4, the wing spoilers on the second wing 3 are located outside the second connecting beam 5, and the first connecting beam 4 and the second connecting beam 5 are symmetrically arranged about the vertical central plane of the fuselage 1.

The beneficial effects of the above alternative embodiment are: the first connecting beam 4 is perpendicular to the extending direction of the first wing 2, and the second connecting beam 5 is perpendicular to the extending direction of the second wing 3, so that the unmanned aerial vehicle can take off and land vertically, the uniformity of lift force is improved, and good flight power is achieved; the wing spoilers are arranged, so that the flight stability is adjusted.

Optionally, as shown in fig. 1 to 8, in some embodiments, the rear spoiler further includes a tail fin, the tail fin 8 is of an inverted V-shaped structure, and end portions of open ends of the inverted V-shaped structure of the tail fin 8 are detachably disposed at rear ends of the first connecting beam 4 and the second connecting beam 5, respectively; two tail spoilers are arranged on the tail wing 8 and are respectively arranged on two side plates of the inverted V-shaped structure.

Alternatively, as shown in fig. 1 to 8, in some embodiments, there are two landing gears 9, two landing gears 9 are detachably connected to the lower portion of the fuselage 1, the landing gears 9 are two-point supporting structures, and two charging seats 12 are installed on two lower end sleeves of each landing gear 9.

In the above alternative embodiment, it should be noted that the undercarriage 9 is in an inverted "V" shape, and the undercarriage 9 is inserted into the charging seat 12 and fastened by bolts.

The beneficial effects of the above alternative embodiment are: through setting up two undercarriage 9, realized the stable support to unmanned aerial vehicle's fuselage 2, had higher stationarity.

Optionally, as shown in fig. 1 to 8, in some embodiments, the undercarriage further includes a connecting rod 10, two ends of the two undercarriages 9 are respectively connected by the connecting rod 10, and the connecting rod 10 is located below the charging seat 12.

In the above optional embodiment, it should be noted that the landing gear further includes a three-way joint, an upper end of the three-way joint is connected to a lower end of the landing gear 9, and the connecting rod 10 is inserted through two ends of a lower side of the three-way joint.

The beneficial effects of the above alternative embodiment are: by providing the connecting rod 10, the stability of the undercarriage is enhanced while also avoiding the charging dock 12 from falling.

Alternatively, as shown in fig. 1-8, in some embodiments, the fuselage 1 is molded from a high strength fiberglass and foam sandwich.

The beneficial effects of the above alternative embodiment are: the flying weight is reduced by arranging the machine body 1 formed by molding the high-strength glass fiber and foam interlayer; the first connecting beam 4 and the second connecting beam 5 are symmetrically arranged about the vertical central plane of the aircraft body 1, so that the stability of the flight power is realized.

Optionally, as shown in fig. 1 to 8, in some embodiments, the charging dock includes a charging dock body 13 and an electrode 21, the electrode 21 is disposed on a lower surface of the charging dock body 13, and the charging dock body 13 is provided with a mounting hole 17 for detachably connecting to an undercarriage of the unmanned aerial vehicle; the lower surface of the charging seat body 13 is provided with a groove 20, and an electrode 21 is arranged in the groove 20; the groove 20 is an open rectangular cross-section groove; the electrode 21 is a rectangular columnar projection, and the electrode 21 is disposed at the center of the groove 20.

In the above optional embodiment, it should be noted that the connection mode between the electrode 21 and the charging seat body 13 may be fixed connection or detachable connection; the mounting holes 17 can be arranged into different shapes according to different unmanned aerial vehicle landing gears; the electrode 21 is a rectangular columnar projection, and the electrode 21 is disposed at the center of the groove 20.

The beneficial effects of the above alternative embodiment are: by arranging the charging seat body 13 and the electrodes 21, the unattended system is more automatic and intelligent, and the labor input is reduced; different connection modes of the electrodes 21 and the charging seat body 13 are set, and the mounting holes 17 are set into different shapes according to different unmanned aerial vehicle undercarriages, so that the unmanned aerial vehicle charging seat can adapt to various working environments and different types of unmanned aerial vehicles; through setting up recess 20 to set electrode 21 to the rectangle column protruding, make unmanned aerial vehicle can be accurate fix a position in the charging process, the charging process is more accurate convenient.

Optionally, as shown in fig. 1 to 8, in some embodiments, the charging base further includes a clamping member 14 and fastening screws 19, the clamping member 14 is mounted on the charging base body 13 through a plurality of fastening screws 19, and the mounting hole 17 is disposed at a connection position of the clamping member 14 and the charging base body 13; the mounting hole 17 is a rectangular hole; a dihedral angle between the plane of the clamping piece 14 and the plane of the charging seat body 13 is an obtuse angle; the clamping piece 14 is of a U-shaped structure, a mounting hole 17 is formed between the open end of the U-shaped structure of the clamping piece 14 and the charging seat body 13, four fixing holes 18 are formed in the clamping piece 14, the fixing holes 18 are stepped holes, and fastening screws 19 are connected with the fixing holes 18 in a threaded manner; the nominal diameter of the tightening screw 19 is between 3mm and 5 mm.

In the above optional embodiment, it should be noted that the mounting hole 17 is a rectangular hole, and a dihedral angle between a plane where the clamping member 14 is located and a plane where the charging seat body 13 is located is an obtuse angle.

The beneficial effects of the above alternative embodiment are: the charging seat body 13 can be conveniently installed and replaced through the clamping piece 14 and the fastening screw 19; by setting the dihedral angle between the plane where the clamping piece 14 is located and the plane where the charging seat body 13 is located to be an obtuse angle, the front surface of the electrode 21 faces downwards, so that the charging operation can be conveniently carried out by contacting a charging electrode in the unmanned airplane cabin; the clamping piece 14 is arranged to be of a U-shaped structure, so that the charging seat body 13 can be conveniently fixed and installed; by providing the fixing hole 18 as a stepped hole, it is possible to avoid the unsightly and inconvenient use caused by the protrusion of the screw head after the fixing screw 7 is installed.

Optionally, as shown in fig. 1 to 8, in some embodiments, the charger further includes a protection cover 15, a positioning hole 16 is formed in the protection cover 15, an installation groove is formed in a surface of the charging seat body 13 facing away from the groove 20, the protection cover 15 is disposed at an open end of the installation groove, and the installation groove is used for installing a circuit board.

In the above-mentioned alternative embodiment, it should be noted that the protection cover 15 is mounted on the mounting groove in a snap-fit manner.

The beneficial effects of the above alternative embodiment are: by arranging the mounting groove, the mounting and the storage of the charging line can be facilitated; the protective cover 15 is provided with a positioning hole 16, and the protective cover 15 is mounted on the mounting groove in a buckling mode, so that the protective cover can be conveniently detached and mounted.

In the specific implementation process, the parameters of the drooping fixed-wing unmanned aerial vehicle are as follows: wingspan: 3200 mm; machine length: 1780 mm; the machine height is as follows: 465mm (without landing gear); standard load: 2 kg; during voyage: more than or equal to 100min (less than 1000 m); working radius: not less than 50Km (1000m or less); measuring and controlling the distance: the microwave link is 50Km/30 Km; working altitude: more than or equal to 3000 m; wind resistance: grade 5 or more; and (3) landing precision: is better than 30 cm; the safety mechanism is as follows: the system self-checking, chain breakage protection, low-power return and autonomous standby landing.

Although the invention has been described in detail with respect to the general description and the specific embodiments, it will be apparent to those skilled in the art that modifications and improvements can be made based on the invention. Therefore, such modifications and improvements are intended to be within the scope of the invention as claimed.

In the present specification, the terms "upper", "lower", "left", "right", "middle", and the like are used for the sake of clarity only, and are not intended to limit the scope of the present invention, and changes or adjustments of the relative relationship thereof are also considered to be the scope of the present invention without substantial changes in the technical content.

Claims (10)

1. A special vertical take-off and landing unmanned aerial vehicle of an unattended system is characterized by comprising a fuselage (1), a first wing (2), a second wing (3), a first connecting beam (4), a second connecting beam (5), a vertical propeller (6), a tail propeller (7), an undercarriage (9), a charging seat (12) and a power breaker (11), wherein the first wing (2) and the second wing (3) are respectively arranged on two sides of the fuselage (1), the first connecting beam (4) is detachably connected on the first wing (2), the second connecting beam (5) is detachably connected on the second wing (3), the vertical propeller (6) is respectively arranged at two ends of the first connecting beam (4) and two ends of the second connecting beam (5), the tail propeller (7) is arranged at the tail part of the fuselage (1), the bottom of fuselage (1) is provided with outage ware (11), the lower surface of fuselage (1) still is provided with undercarriage (9), the lower extreme of undercarriage (9) is provided with charging seat (12).

2. The unmanned aerial vehicle for unmanned aerial vehicle system of claim 1, further comprising a tail (8), wherein the tail (8) is detachably connected to the rear ends of the first connecting beam (4) and the second connecting beam (5); the first connecting beam (4) is perpendicular to the extending direction of the first wing (2), and the second connecting beam (5) is perpendicular to the extending direction of the second wing (3); the first connecting beam (4) is connected to the middle of the first wing (2) through a bolt, and the second connecting beam (5) is connected to the middle of the second wing (3) through a bolt.

3. The UAV of claim 2, wherein each of the first wing (2) and the second wing (3) has a wing spoiler disposed thereon, the wing spoilers of the first wing (2) are disposed outside the first connecting beam (4), the wing spoilers of the second wing (3) are disposed outside the second connecting beam (5), and the first connecting beam (4) and the second connecting beam (5) are symmetrically disposed about the vertical central plane of the fuselage (1).

4. The unmanned aerial vehicle special for take-off and landing of the unmanned system as claimed in claim 3, further comprising a tail spoiler, wherein the tail wing (8) is of an inverted V-shaped structure, and the ends of the open ends of the inverted V-shaped structure of the tail wing (8) are detachably arranged at the rear ends of the first connecting beam (4) and the second connecting beam (5), respectively; the tail wing (8) is provided with two tail spoilers which are respectively arranged on two side plates of the inverted V-shaped structure.

5. The unmanned aerial vehicle for vertical take-off and landing of an unmanned on duty system according to claim 1, wherein there are two landing gears (9), the two landing gears (9) are detachably connected to the lower portion of the body (1), the landing gears (9) are two-point supporting structures, and the charging seat (12) is installed on the two lower end sleeves of each landing gear (9).

6. The unmanned aerial vehicle for unmanned aerial vehicle system of claim 5, further comprising a connecting rod (10), wherein two ends of the two landing gears (9) are respectively connected through the connecting rod (10), and the connecting rod (10) is located below the charging seat (12).

7. The unmanned aerial vehicle for unmanned aerial vehicle dedicated to take-off and landing according to claim 1, wherein the fuselage (1) is molded from high strength fiberglass and foam sandwich.

8. The unmanned aerial vehicle special for unmanned system of claim 1, wherein the charging base comprises a charging base body (13) and an electrode (21), the electrode (21) is arranged on the lower surface of the charging base body (13), and the charging base body (13) is provided with a mounting hole (17) for detachable connection to the landing gear of the unmanned aerial vehicle; a groove (20) is formed in the lower surface of the charging seat body (13), and the electrode (21) is arranged in the groove (20); the groove (20) is an open rectangular cross-section groove; the electrode (21) is a rectangular columnar bulge, and the electrode (21) is arranged at the center of the groove (20).

9. The unmanned aerial vehicle special for unmanned system of claim 8, further comprising a clip (14) and fastening screws (19), wherein the clip (14) is mounted on the charging seat body (13) through a plurality of fastening screws (19), and the mounting holes (17) are disposed at the connection between the clip (14) and the charging seat body (13); the mounting hole (17) is a rectangular hole; a dihedral angle between the plane of the clamping piece (14) and the plane of the charging seat body (13) is an obtuse angle; the clamping piece (14) is of a U-shaped structure, the mounting hole (17) is formed between the open end of the U-shaped structure of the clamping piece (14) and the charging seat body (13), four fixing holes (18) are formed in the clamping piece (14), the fixing holes (18) are stepped holes, and fastening screws (19) are connected to the fixing holes (18) in an internal thread mode; the nominal diameter of the fastening screw (19) is between 3mm and 5 mm.

10. The unmanned aerial vehicle special for take-off and landing of the unattended system according to claim 9, further comprising a protective cover (15), wherein the protective cover (15) is provided with a positioning hole (16), a mounting groove is formed on the surface of the charging seat body (13) deviating from the groove (20), the protective cover (15) is arranged at the open end of the mounting groove, and the mounting groove is used for mounting a circuit board.

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